Quick-release and quick-assembly chair leg lock for an aircraft seat

Abstract

The utility model belongs to the technical field of seat, and relates to a quick detachable and quick mounted chair leg lock of aviation seat, is provided with the T type slide way of opening upwards on guide rail, is provided with arc slot on the opposite two side walls of T type slide way, the upper surface of guide rail is provided with lock body, the bottom of lock body is fixed with sliding block, is provided with the first recess of upwards on the bottom surface of lock body, is provided with the vertical screw hole on the upper wall of first recess, is provided with the limiting block of sliding on the upper surface of guide rail in first recess, the lower part of lifting bolt is step shaft, the outer thread of middle part is screwed on screw hole, the step shaft of lower part is connected with the step hole on limiting block, and the limiting piece that the lifting bolt is separated from limiting block is provided at the place of extending the bottom surface of limiting block, the mounting hole that can be connected with the chair leg of aviation seat is provided on lock body, the advantages are: simple structure, convenient operation, safe and reliable, conform to the airworthiness specification, be applicable to the quick detachable and quick mounted of aviation seat.

Description

Technical Field

[0001] This utility model belongs to the field of aviation seat technology, and in particular relates to a quick-release and quick-installation seat leg lock for aviation seats. Background Technology

[0002] In modern civil aircraft, aircraft seats, as one of the core components of the cabin, must meet requirements for airworthiness, safety, reliability, and maintainability. Traditional aircraft seat fixing methods mostly use bolt-fastening or snap-on structures, which are complex and time-consuming to install and remove, especially in emergency situations (such as seat malfunction, repair, or replacement), making rapid response difficult. Furthermore, traditional structures suffer from low assembly precision, susceptibility to loosening, and inconvenient operation, affecting maintenance efficiency and passenger experience. In addition, traditional connection mechanisms are prone to loosening under impact loads (such as emergency landings or turbulence), compromising structural safety.

[0003] Although some quick-release devices are used in existing technologies, they generally suffer from defects such as complex structure, insufficient reliability, and poor adaptability, making it difficult to simultaneously meet the requirements of quick disassembly and assembly, high strength load-bearing capacity, and compliance with airworthiness and safety standards. Summary of the Invention

[0004] The purpose of this invention is to provide a quick-release and quick-install leg lock for an aircraft seat that is simple in structure, easy to operate, safe and reliable, and conforms to aviation airworthiness standards.

[0005] The purpose of this utility model is to solve the following problem:

[0006] A quick-release and quick-install leg lock for an aircraft seat includes a guide rail with an upward-facing T-shaped slide. Corresponding arc-shaped grooves are spaced along the length of the opposite side walls of the T-shaped slide. A lock body slides onto the upper surface of the guide rail. A slider that can slide within the T-shaped slide and disengage from the two opposite arc-shaped grooves, and an upward-facing first groove are fixed to the bottom surface of the lock body. A vertical threaded hole is provided on the upper wall of the first groove, and a limiting block that can slide on the upper surface of the guide rail is provided within the first groove. The lower part of the lifting bolt is a stepped shaft that is wider at the top and narrower at the bottom. The external thread in the middle of the lifting bolt is screwed into the threaded hole, and the stepped shaft at the top and bottom matches the stepped hole on the limit block, which is larger at the top and smaller at the bottom. A limit member is provided at the bottom surface of the limit block to prevent the lifting bolt from disengaging from the limit block. Rotating the lifting bolt can make the limit block abut against the upper surface of the guide rail and the slider abut against the upper surface of the T-shaped slide groove, thus locking the limit block on the guide rail. Reversing the lifting bolt can loosen the limit block from abutting against the slide, and the slider can slide in the T-shaped slide and leave the guide rail from the arc groove. The lock body is provided with mounting holes that can be connected to the legs of the aircraft seat.

[0007] As a further optimization of the above technical solution, the limiting component is a cylindrical pin, and a transverse pin hole is provided on the stepped shaft extending from the bottom surface of the limiting block. The cylindrical pin is inserted into the pin hole to achieve the limiting.

[0008] As a further optimization of the above technical solution, the limiting component is a self-locking nut, and an external thread is provided on the stepped shaft extending from the bottom surface of the limiting block. The self-locking nut is screwed onto the external thread to achieve the limiting.

[0009] As a further optimization of the above technical solution, the top of the lifting bolt is provided with a polygonal prism groove in the center to facilitate the rotation of the lifting bolt with a special tool.

[0010] As a further optimization of the above technical solution, the polygonal prism groove is a hexagonal prism groove.

[0011] As a further optimization of the above technical solution, the slider has an upward-facing cylinder centrally located on the upper surface of the disc. The cylinder has an external thread and is screwed onto the internal thread groove of the lock body through the external thread. The outer diameter of the disc is greater than the distance between the two opposite side walls of the T-shaped slide and less than or equal to the inner diameter of the two opposite arc grooves.

[0012] As a further optimization of the above technical solution, the lock body has two internal thread grooves, which are respectively set on the front and rear sides of the lock body, and there are also two corresponding sliders, which are respectively screwed onto the two internal thread grooves of the lock body.

[0013] As a further optimization of the above technical solution, the bottom surface of the limiting block is provided with downwardly extending C-shaped protrusions on both sides, the step shaft is located between the two C-shaped protrusions, the openings of the two C-shaped protrusions are opposite to each other, and the C-shaped protrusions and the slider are an integral structure.

[0014] As a further optimization of the above technical solution, the upper surface of the limiting block is provided with a downward-facing second groove.

[0015] As a further optimization of the above technical solution, the thickness of the limiting block is less than the height of the first groove, so that the limiting block can move up and down within the first groove.

[0016] The advantages of this invention compared to the prior art are:

[0017] 1. Quick disassembly and assembly: The entire disassembly and assembly process of this utility model can be completed by simply rotating the lifting bolt with an Allen wrench. No other special tools are required, making it suitable for maintenance personnel to quickly replace seats.

[0018] 2. High load-bearing capacity: The lock body and slider of this utility model are made of high-strength aluminum alloy or titanium alloy materials, and with the cylindrical pin and limit block structure, it can meet the static and dynamic strength requirements of mainstream aviation seats.

[0019] 3. Precise positioning: The limiting block of this utility model cooperates with the cylindrical surface of the guide rail to ensure that the seat does not deviate in the front-back and left-right directions, thus improving efficiency and safety.

[0020] 4. Anti-detachment design: The cylindrical pin prevents the limit block and lifting bolt from accidentally coming off, ensuring that no errors occur during disassembly and assembly.

[0021] 5. Easy to maintain: The components of this utility model adopt a modular design, which facilitates replacement and maintenance and reduces life cycle costs.

[0022] 6. Strong compatibility: This utility model is applicable to different models of aircraft seats, improving its versatility. Attached Figure Description

[0023] Figure 1 This is a three-dimensional schematic diagram of the present invention.

[0024] Figure 2 This is a top view of the present invention.

[0025] Figure 3 yes Figure 2 Enlarged cross-sectional view along the AA direction.

[0026] Figure 4 yes Figure 2 Enlarged cross-sectional view of the BB direction.

[0027] Figure 5 yes Figure 2 Enlarged cross-sectional view along the CC direction.

[0028] Figure 6 This is a three-dimensional schematic diagram of the guide rail of this utility model.

[0029] Figure 7 This is a three-dimensional schematic diagram of the lock body of this utility model.

[0030] Figure 8 This is a three-dimensional schematic diagram of the lock body, limit block, and slider of this utility model after assembly. Detailed Implementation

[0031] The present invention will be further described below with reference to the accompanying drawings and specific embodiments. See also: Figures 1-8 :

[0032] A quick-release and quick-install leg lock for an aircraft seat includes a guide rail 10. The guide rail 10 has an upward-facing T-shaped slide rail 11. Corresponding arc-shaped grooves 13 are spaced apart along the length of the opposite side walls 14 of the T-shaped slide rail 11. A lock body 20 is slidably mounted on the upper surface 12 of the guide rail 10. A slider 50, which can slide within the T-shaped slide rail 11 and disengage from the two opposite arc-shaped grooves 13, and an upward-facing first groove 22 are fixed to the bottom surface of the lock body 20. A vertical threaded hole 24 is provided on the upper wall of the first groove 22. A limiting block 40, which can slide on the upper surface of the guide rail 10, is provided within the first groove 22. The lower part of the lifting bolt 30 is a stepped shaft 32, wider at the top and narrower at the bottom. The external thread in the middle of the lifting bolt 30 is screwed into the threaded hole, and the stepped shaft 32 at the top and bottom is matched and connected to the stepped hole 44 on the limiting block 40, which is larger at the top and smaller at the bottom. A limiting member is provided at the bottom surface of the limiting block 40 to prevent the lifting bolt 30 from disengaging from the limiting block 40. Rotating the lifting bolt 30 can make the limiting block 40 abut against the upper surface of the guide rail 10 and the slider 50 abut against the upper surface of the transverse groove of the T-shaped slide 11, thereby locking the limiting block 40 onto the guide rail 10. Reversing the lifting bolt 30 can loosen the limiting block 40 from the slide, and the slider 50 can slide in the T-shaped slide 11 and leave the guide rail 10 from the arc groove 13. The lock body 20 is provided with a mounting hole 21 that can be connected to the leg of the aircraft seat.

[0033] As a further optimization of the above technical solution, the limiting component is a cylindrical pin 33. A transverse pin hole is provided on the stepped shaft 32 extending out of the bottom surface of the limiting block 40, and the cylindrical pin 33 is inserted into the pin hole to achieve the limiting.

[0034] As a further optimization of the above technical solution, the limiting component is a self-locking nut. The stepped shaft 32 extending out of the bottom surface of the limiting block 40 is provided with an external thread, and the self-locking nut is screwed onto the external thread to achieve the limiting.

[0035] As a further optimization of the above technical solution, the top of the lifting bolt 30 is provided with a polygonal prism groove 31 to facilitate the rotation of the lifting bolt 30 with a special tool.

[0036] As a further optimization of the above technical solution, the polygonal prism groove 31 is a hexagonal prism groove.

[0037] As a further optimization of the above technical solution, the slider 50 has an upward-facing cylinder 52 centrally located on the upper surface of the disc 51. The cylinder 52 has an external thread and is screwed onto the internal thread groove 23 of the lock body 20 through the external thread. The outer diameter of the disc 51 is greater than the distance L between the two opposite side walls 14 of the T-shaped slide 11 and less than or equal to the inner diameter D of the two opposite arc grooves 13.

[0038] As a further optimization of the above technical solution, the lock body 20 has two internal thread grooves 23, which are respectively set on the front and rear sides of the lock body 20, and there are also two corresponding sliders 50, which are respectively screwed onto the two internal thread grooves 23 of the lock body 20.

[0039] As a further optimization of the above technical solution, the bottom surface of the limiting block 40 is provided with downwardly extending C-shaped protrusions 43 on both sides, the step shaft 32 is located between the two C-shaped protrusions 43, the openings of the two C-shaped protrusions 43 are opposite to each other, and the C-shaped protrusions 43 and the slider 50 are an integral structure.

[0040] As a further optimization of the above technical solution, the upper surface of the limiting block 40 is provided with a downward-facing second groove 41.

[0041] As a further optimization of the above technical solution, the thickness of the limiting block 40 is less than the height of the first groove 22, so that the limiting block 40 can move up and down within the first groove 22.

[0042] The above embodiments are only used to illustrate the technical solutions of this utility model, and are not intended to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that simple substitutions or modifications can still be made to the technical solutions or technical features described in the foregoing embodiments, and these simple substitutions or modifications do not cause the essence of the corresponding technical solutions to deviate from the spirit and substance of the technical solutions of the embodiments of this utility model, and are still within the protection scope of this utility model.

Claims

1. A quick-release and quick-install leg lock for an aircraft seat, comprising a guide rail, characterized in that: The guide rail is provided with an upward-opening T-shaped slide. Corresponding arc-shaped grooves are spaced along the length of the opposite side walls of the T-shaped slide. A locking body is slidably mounted on the upper surface of the guide rail. A slider that can slide within the T-shaped slide and disengage from the two opposite arc-shaped grooves, and an upward-facing first groove are fixed to the bottom surface of the locking body. A vertical threaded hole is provided on the upper wall of the first groove, and a limiting block that can slide on the upper surface of the guide rail is provided within the first groove. The lower part of the lifting bolt is a stepped shaft that is wider at the top and narrower at the bottom. The external thread in the middle of the lifting bolt... The stepped shafts connected to the upper and lower parts of the threaded hole are matched and connected to the stepped holes with larger upper parts and smaller lower parts on the limiting block. A limiting component is provided at the bottom surface of the limiting block to prevent the lifting bolt from disengaging from the limiting block. Rotating the lifting bolt can make the limiting block abut against the upper surface of the guide rail and the slider abut against the upper surface of the T-shaped slide groove, thus locking the limiting block on the guide rail. Reversing the lifting bolt can loosen the limiting block from the slide groove, allowing the slider to slide in the T-shaped slide and leave the guide rail from the arc groove. The lock body is provided with mounting holes that can be connected to the legs of an aviation seat.

2. The quick-release and quick-install leg lock for an aircraft seat according to claim 1, characterized in that: The limiting component is a cylindrical pin. A transverse pin hole is provided on the stepped shaft extending from the bottom surface of the limiting block. The cylindrical pin is inserted into the pin hole to achieve the limiting.

3. The quick-release and quick-install leg lock for an aircraft seat according to claim 1, characterized in that: The limiting component is a self-locking nut. The stepped shaft extending from the bottom surface of the limiting block is provided with an external thread, and the self-locking nut is screwed onto the external thread to achieve the limiting.

4. The quick-release and quick-install leg lock for an aircraft seat according to claim 1, characterized in that: The top of the lifting bolt is provided with a polygonal prism groove in the center to facilitate rotation of the lifting bolt with a special tool.

5. The quick-release and quick-install leg lock for an aircraft seat according to claim 4, characterized in that: The polygonal prism groove is a hexagonal prism groove.

6. The quick-release and quick-install leg lock for an aircraft seat according to claim 1, characterized in that: The slider has an upward-facing cylinder centrally located on the upper surface of the disc. The cylinder has external threads and is screwed onto the internal thread groove of the lock body via the external threads. The outer diameter of the disc is greater than the distance between the two opposite side walls of the T-shaped slide and less than or equal to the inner diameter of the two opposite arc grooves.

7. A quick-release and quick-install leg lock for an aircraft seat according to claim 6, characterized in that: The lock body has two internal threaded grooves, which are respectively located on the front and rear sides of the lock body. There are also two corresponding sliders, which are screwed onto the two internal threaded grooves of the lock body.

8. The quick-release and quick-install leg lock for an aircraft seat according to claim 1, characterized in that: The bottom surface of the limiting block is provided with downwardly extending C-shaped protrusions on both sides. The step shaft is located between the two C-shaped protrusions, and the openings of the two C-shaped protrusions face each other. The C-shaped protrusions and the slider are an integral structure.

9. A quick-release and quick-install leg lock for an aircraft seat according to claim 8, characterized in that: The upper surface of the limiting block is provided with a downward-facing second groove.

10. A quick-release and quick-install leg lock for an aircraft seat according to claim 1, characterized in that: The thickness of the limiting block is less than the height of the first groove, so that the limiting block can move up and down within the first groove.

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